IqATIONAL AERONAUTICS AND SPACE ADMINISTRATION wc) 9-41',sTELS.WASHINOTON DC 20546 WO _-6925

FOR RELEASE: MONDAY P.M.November 29, 1965

RELEASE N0:65-362

PROJECT:a :Nr 716

CONTENTS

Title Page

GENERAL NEWS RELEASE .................. =......... 1-3

Launch Vehicle Countdown ........................ 4

Nominal Mission Plan - Gemini 7 ................. 5-6Gemini 7 Experiments .................. ...... =---7-14

Experiments Flown on Earlier Missions ........ 7In-Flight Exerciser .......................... 7-8In-Flight Phonocardiogram .................... 8Bone Demineralization ........................ 8-9Human 0tolith Function ....................... 9Proton-Electron Spectrometer ................. 9-10Tri-Axis Magnetometer ........................ i0Celestial Radiometry Space Object Radiometry-10-11Simple Navigation ............................ ii

K Synoptic Terrain Photography ................. 11-12

Synoptic Weather Photography ................ -12Visual Acuity Astronaut Visibility ........... 12-14

Experiments to be Flown for the First Time ...... 15-20Bioassays Body Fluids ..... z.................. 15Calcium Balance Study ........................ 15In-Flight Sleep Analysis ..................... 15-16Optical Communication ........................ 16-18Landmark Contrast Measurements ............... 18

Star Occultation Navigation .................. 18-20Camera Equipment for Gemini 7 and 6 Missions .... 21-22

16 MM Maurer Movie Camera .................... 2170 MM Hasselblad Camera ...................... 22

Gemini 7 to be launched no earlier than Dec. 4, 1965.

Gemini 6 to be launched nine days later

-more-

/

-2-

Gemini 7 Fourteen Day Menu Cycle ................ 23-24Menu I, Menu II .............................. 23Menu III, Menu IV ............................. 24

Gemini 6 Launch Preparations .................... 25-28Launch Vehicle Countdown - Gemini 6 ............. 29Nominal Mission Plan - Gemini 6 ................. 30-34

Launch Windows ............................... 30Gemini 6 and 7 Rendezvous Orbit Geometry ..... 32

Gemini 6 Experiments ............................. 35Gemini 6 Menu ................................... 36-37Manned Space Flight Network Gemini 6 and 7Missions ........................................ 38-39

Prime Computing Support ...................... 38Other Computer Support ....................... 38-39Network Readiness ............................. 39

Tracking Two Manned Spacecraft .................. 39-40Orbits - Revolutions ............................ 41Crew Training Background ........................ 42-43Immediate Pre-Flight Crew Activities ............ I_4-45

Flight Activities ............................ 45Crew Safety ...................................... 46-47

Survival Package .............................. 46-47Gemini 6 Suit .................................... 48

Gemini 7 Suit .................................... 49Medical Checks ................................... 50Body Waste Disposal .............................. 50Food ............................................ 50-51Weather Requirements ............................ 52Planned and Contingency Landing Areas ........... 53Gemini Spacecraft ................................ 54-59

Reentry Module ................................ 54Adapter Section .............................. 54

Propellant ...................................... 59Rendezvous Radar ................................ 59-60Electrical Power Systems ........................ 60-63

Gemini 7 ...................................... 60-61Gemini 6 ..................................... 61

_el Cell Diagrams .......................... 62-63Gemini Launch Vehicle ........................... 64-65Crew Biographies ................................. 66-74Previous Gemini Flights ......................... 75-77Project Officials ............................... 78U.S. Manned Space Flights (chart) ............... 79Spacecraft Contractors .......................... 80-81

NOTE TO EDITORS:

Supplemental information will be released asrapidly as it develops.

-more-

NEWS wo_4,5,NA11ONAL AERONAUTICS AND SPACE ADMINISTRATION TELS. WO '3-6925WASHINGTON, D.C. 20546

FOR RELEASE: MONDAY P.M.November 29, 1965

RELEASE NO: 65-362

GEMINI?/6 FLIGHT

TO ATTEMPT RENDEZVOUS,

LONG DURATION MISSIONS

Within the next three weeks, the National Aeronautics and

Space Administration is scheduled to carry out two manned

space missions--a long-duration flight of up to 14 days and

rendezvous of two Gemini spacecraft.

Gemini 7, a long-duration flight, is scheduled to be

launched no earlier than Dec. 4.

Gemini 6, which will rendezvous with Gemini 7, is to be

launched nine days later, Dec. 13.

Success in the two flights will represent:

i. The longest U.S. manned flight to date (Gemini 5

Astronauts L. Gordon Cooper and Charles Conrad were in flight

190 hours and 56 minutes, nearly eight days).

2. The first space rendezvous of two manned maneuverable

spacecraft.

-more- 11/23/65

--2--

3. A minimum turn-around time for launch of two missions

from the same pad.

Despite the rendezvous objective of Gemini 6, the two

missions will be carried out independently. That is, Gemini 7

will be launched and carried out as originally planned. No

major changes have been made in the Gemini 7 flight plan.

The Gemini 6 mission will be carried out according to a

flight plan which is nearly identical to the one prepared for

the Oct. 25 launch which was postponed when the Agena Target

Vehicle failed to achieve orbit. The only major change is that

the Gemini 6 spacecraft was to have docked with the Agena.

In the forthcoming flight, the two Gemini spacecraft will

not be physically connected.

It was decided that the planned schedule of Gemini 7 and the

availability of the Gemini 6 launch vehicle and spacecraft

(already oheoked out on Pad 19) presented an opportunity to

carry out a rendezvous of two manned vehicles.

-more -

-3-

The first several days of the Gemini 7 mission will be

devoted to carrying out experiments. At about five days the

crew will maneuver the spacecraft into a target orbit for

Gemini 6. During the rendezvous attempt by Gemini 6, the

Gemini 7 crew will maintain their orbit and spacecraft attitude,

performing only those maneuvers required to make themselves a

better target.

Following a successful liftoff, Gemini 6 immediately will

begin maneuvers to achieve rendezvous which isplanned for its

fourth orbit. Following rendezvous, Gemini 6 will station keep

(fly formation) on Gemini 7 for about two revolutions. Subse-

quently, Gemini 7 will fly formation on Gemini 6 for one space-

craft day, about 40 minutes.

Gemini 6 will reenter the Earth's atmosphere and land in the

West Atlantic Ocean after about 46 hours and 45 minutes, at ap-

proximately 8:20 a.m. EST.

Gemini 7 duration will be about 329 hours and 30 minutes,

landing in the same area at approximately 8 a.m. EST, two days

later.

(BACKGROUND INFORMATION FOLLOWS)

-more-

-4-

LAUNCH VEHICLE COUNTDOWN

Gemini 7

F-3 days Start pre-count

F-1 day Start mid-count

T-12 hours GLV propellant loading

T-390 minutes Complete propellant loading

T-300 minutes Begin terminal countdown

T-120 minutes Flight Crew to Complex 19

T-lO0 minutes Crew enters spacecraft

T-75 minutes CloSe spacecraft hatches

T-50 minutes White Room evacuation

T-35 minutes Begin erector lowering

T-15 minutes Spacecraft OAMS static firing

T-O4 seconds GLV ignition

T-O seconds Liftoff

T+2 minutes, 36 seconds Booster engine cutoff (BECO)

T+5:41 Second stage engine cutoff (SECO)

T+6:ll Spacecraft-launch vehicle separation

-more-

t

-5-

NOMINAL MISSION _L_

Qe_ini-7

Gemini-7 is scheduled to be launched from Complex 19, Cape Kennedy

at about e:3opmEST,December 4. It will be launched into an elliptical

orbit with an apogee of 210 miles and 8 perigee of I00 miles. The

orbit will be inclined 28.87 degrees rio the equator.

The spacecraft is to separate from the booster 30 seconds _fter

sustainer engine cutoff.

Immediately following spacecraft separation, the spacecraft will

turn around to blunt end forwsrd, and begin station keeping on the

booster second stsge. Station keeping will continue for sbout 25

minutes ground elapsed time (GET) from liftoff. This time extends

into about five minutes before the first darkness period.

Celestial radiometry experiments will be conducted during the

remainder of the first darkness period.

AS three hours, 50 minutes after lift-off as the spacecraft is

at its third apogee, thrusters will be fired in a posigrade maneuver

to raise the perigee to 12£ miles. This m_neuver establishes a space-

craft orbital lifetime of 15 days.

The next several days of the flight will be devoted to conducting

assigned experiments.

At about five days in flight the crew will circularize the spece-

craft orbit to provide the proper target orbit for Gemini 6. The exact

maneuvers required will depend on the decay rate of the Gemini 7 orbit

and the expected liftoff ti_J_ of Gemini 6, now planned for eight d_ys,

19 hours and four _,inutes following Gemini 7 liftoff.

-more-

|,

-6-

Under present plans, circularization msneuvers will be performed

120 hours after lift-off of the Gemi_ 7 spscecrafto The crew will give

the spscecraft a posigrsde thrust at apogee. This will result in

change of velocity of 1OO feet per second and circularizstion st 185

miles.

The rendezvous portion of the Gemini 6 and Gemini 7 spececrsft is

described in the Gemini 6 Nominal _ission _lsn.

The remsining Gemini 7 experiments will be conducted following

completion of rendezvous activities. The Gemini 7 crew will initiate

retrofire near the end of the 206 th revolution. Landing will be Jn

the West Atlantic recovery szes st the beginning of the 2OTth revolution.

-more-

-7-

G_MINI 7 mXPE_.Ik_';NTS

Twenty experiu,ents are scheduled for Gemini 7. Fourteen ere

continuing experi_:,ents end hsve been csrried sbosrd previous Gemini

flights, in repeating these over 8 number of manned spsce flight

missions, experi_,sters hope to gsin date covering s ntm,ber cf subjects

under varying flight conditions.

.%esults of the experiments carried sbo_rd Gemini missions J

and 4 were presented st a symposium in Wsshington esrly this fell.

3Jmilsr sym pc s ia will be held perlodic_lly during the msnned sp_ce

flight program.

_Lxperiments Flown on Ear$ier Pdssions

1. Cardiovasculsr Conditioning (5)*

This experi_ent will determine the effectiveness of cyclic Jnflr-

tions of pneumstic cuffs on the thighs ss e preventive meesure of

cardiovascular deeonditionJng (heart snd blood distribution system)

induced by prolonged weightlessness. The cuffs are built into the

spscesuit sround the thighs 8nd infleted periodicelly to 80_sJ of

_,ercury pressure, incressing blood pressure below the cuffs. Th_

automstic pressurization cycle lssts two minutes out of every six _nd

uses oxygen from the enviro_ental control systen_.

2. in-Flight Exerciser (4 snd 5)

The objective of this experiment is to sssess the sstron_uts'

capsci_y to perfom_ physicsl work 8nd their cspability for sustsin_d

performance. The rapidity with which the hesrt rste returns to ncrme]

*ind" c_:te_ prev_ ous Gemini mission

-_ore --

-8-

after cessetion of exercise is an indication of an indiv_du_l's

physical fitness. A workload will be provided by specific periods

of exercise st the rate of one pull per second for 30 _econds on an

exercise device that requires s known sn_otmt of effort.

The exercise device consists of e p_r of bungee cords attached

to e nylon handle st one end and a nylon foot strop st the other end.

fhe in-flight deta obtained will be colJ,peredwith the control

data to determine the cepecity for work in spece.

3. In-_li_ht Phonopardiogrsm (4 and 5)

in this experiment the fatigue state of en astronaut's heart

muscle will be deteyn_ned by _,easuring the time _nterv_l between the

activation cf a _uscle end the onset of its contraction.

A microphone will be epplied to sn estron_:ut's chest well _t the

cardiac apex. Heart sounds detected during the flight will be recorded

on sn onbosrd biomedical recorder. The sound trace will be eompored

to the waveform obteined froJ_;e slmulteneous inflight elec_rocgrdiogram

to deter_.ine the time interval between electrical activetion of the

heart muscle and _he onset of Ventriculsr systole.

4. Bone De_dnoralizatiqn (& and ))

The purpose of this experiment is to establish the occur_nce end

degree of bone demineralisation influenced by the rel_tive h,,m_obJliz_-

tion associated with the cockpit of the G_mini spscecreft and weight-

lessness.

_pecial X-rays will be token of en astroneut's heel bone end the

terminal bone of the fifth digit of the right hend. Three pro-flight

-more- _ ......

-9-

and three post-flight exposures will be taken of these two bones _nd

compared to determine if any bone demineralization has occurred due to

the spece flight.

The equipment to be used in this experiment will be closely

calibreted clinicel X-ray machines, stendard ll-lnch by 14-inch X-rey

films and calibrated wedge densitometers.

5. Human _tolith _unction (5)

A visual tester will be used to detern_ne the _stron_uts orienta-

tion capability during flight. The experiment will me_sure changes in

otolith (gravity gradient sensors in the i_er ear) functions.

The tester is a p_ir of special light proof goggles, one eye

piece of which contains a light source in the form of a movable white

line. The astronaut positions the white line with a c_librated knurled

screw to what he judges to be the r_ght pitch axis of the spacecraft.

The second astronaut then reads and records the numbers.

6. P_roton-_lect_n_S_ectrometer (4)

In order to determine the degree of hazard, if any, to which the

crew will be subjected on space flight, it is necessary to project

what radiation environment any given mission will encounter. Specif-

icelly, this experiment will meke measurements outside of the sp_ce-

craft in a region where the inner Ven Allen rediation belt dips close

_o the earth's surface due to the irregular strength of the e_rth's

magnetic field. This region is usually referred tc Ps the South

Atlantic Geomagnetic Ano_mly.

-more-

-iO-

This measurement will be accomplished by means of a scintJllati_g-

crystal, charged-psrticle analyzer mou_]ted on the _dapter assembly of

the spacecraft. Data from this experiment will be used to correlate

rmdie_icn _,easure_ents made inside the spacecraft _nd to predict r_d]_t]on

levels on future space n,ission.

7. Tri-Axis _agnetometer (&)

The purpose of this experiment is to monitor the direction and

a_plitude of the earth's magnetic field with respect to pn orbStlng

spacecraft. The astronauts will operate en adepter-_,ounted tri-sxis

fluxgate ,mgneto_,_eter ss they pass through the South Atlantic Geomag-

netic Anomaly. The magnitude of the three directions of the e_rth's

magnetic field will be measured with respect to the spacecraft. The

measurement will be performed in conjunction with the Proton Electron

Spectrometer experiment to determine the fie]d, line direction and

pitch angle of the impacting p_rticles.

8. Celestial rmdiometry

Space Object ?_diometry (5)

The results of these experiments will provide information on

radiation intensity of celestial bodies and various objects in space.

Instrtm,entation includes a three-channel spectro-rsdiometer, _ dual-

channel _ichelson Interferometer-Spectrometer, and a cryogenically

cooled spectrometer. The equipment can measure radiant intensity from

the ultra-violet through the infrared region. The sensing units _re

housed in the Gemini adapter section and ere directed toward the

objective by orienting the spacecraft.

-more-

-ll-

The objectives for these experiments are to determine the onset

of sensitivity values for earth objects and sky b_ckground radiation

and radiation signatures of various objects in space and on the ground.

Observations will include exhaust pltm_esof rocket vehicles

launched fro_ the _astarn or Western 'resti_nges, rocket sled exhausts

at Hollor,,anAir Force Base, volcanoes and forest fires as well rs

contrasting background areas such as deserts and warm ocean currents.

9. _imple Navigation (4)

The cap_.bilityof man to navigate in space and to provide a

reliable navigation system independent of ground support will be

tested in this experiment. _o special instruments have been developed

for use on Gemini spacecraft to allow detailed menu_l-vlsu_.lexamination

of the space phenomena thought to be best for space navigation purposes.

These are a space stadimeter and a sextant. This flight w_ll only

carry the space sextant w_th which the astronaut will use to make

star-horizon angular measurelr_entsfor orbit_l orient_tlon deter_tlin_tions.

The results will be co1_paredwith actual measurements to det(_rmine

the accuracy of the procecures.

lO. Synoptic Terrain _'hotogroR_hxh(4 and })

The purpose is to obtain photos of selected parts of earth's

surface for use in research in geology, geophysics, geography, oceFn-

ography. This experiment has been flown on every flight since MA-8.

Experiment -- 70mm Hasselblad camera with 80mm Zeiss F2.8 lens;

two packs of color film with 65 exposures each. Approximately n_nety

-more -

pictures will be taken over aress of tileworld, rr_msry eress ere

the shallow wsters around the _ehsmes, the Red See, end the west

central portion of _exico.

ll. Synoptic Weather Photography (3,4 end 5)

The Synoptic Westher Photogrsphy experiment is designed to mske

use of man's _bil_ty to photogrsph cloud systems selectively--in

color and in greater detsil _hsn cen be obLein_d from the current

TIROS meteorological satellite.

A primary purpose of the experiment Js to sugment informetion

from meteorologicsl s_tellites which ere contributing substentielly to

knowledge of the earth's westher systems. In many tress they provide

information where few or no other observstions exist.

_xperiment -- 70_ Hasselblad ostlers with 80nm Zeiss F2.8 lens;

two magazines of color film with 65 exposures esch. Areas of Interest --

_uell line clouds, thunderstorm _ctivity not sssocisted with squall

lines, frontsl clouds end views of fronts, jetstresm cirrus clouds,

typical morning stretus of Gulf states, cosstsl cloudiness, tropic_l

and extratroplcsl cyclones, intertropic_l convergence zone, cellulsr

pettern in subtropicsl phenomenon, wsve clouds induced by islends end

mountain ranges, brosd banking of clouds in the trade winds or other

regions.

12. Visual Acu_t_

Astronaut Visibil_t_ (5)

The visusl ability of the _stron_uts in the detection _nd recog-

nition of objects on the earth's surface will be tested in these experJ-

-more-

.-13-

ments. The spececraft will be equipped with _ visicn tester _nd

photo_,eter. The astronauts will use the vision tester t_ evaluate

visual sightings from space relative to e_rthbound b_seline _lues.

I I I I ' I II I I I I I II I i I I iI I I I ', I iI I i I , i IL ..... J L ..... J L ..... _ L.___-J

I\EIIl,I ![' IJ -II,llJl

,11 1 II']-mOi_O -

-i_.

The photo_eter will _e_sure light Bttenu_tion of the spscecr_f_ window

due ho scsttering. While the spscecraft is oriented the sstron_uts

will view s pattern of p_nels lsid out near Lsredo, Tex_s _nd record

their findings. Viewings will be correlated w_th laborstory experiments

and vision will be checked pre- end post-flight.

During passage of the spacecraft over the sites, the cox1_1_nd

astronaut shall be responsible for msintsining the proper spscecraft

attitude while the second asSronsut observes the target eree end m_kes

verbal com_,ents to the principal investigator st the site.

_or five minutes in each 2& hour period, esch 8stroneut will use

the on-board vision tester to test his own visusl acuity on an opportun-

ity bas_s.

EXPERIMENTS TO BE FLOWN FOR THE FIRST TIME

1. Bioassays Bod_ Fluids

In this experiment the astronauts reaction to stress during space

flight will be studied by means of analysing body fluids. Pre-flight

and post-flight blood samples will be taken. In-flight urine will be

measured at each voiding and a portion of this stored in special bags.

From analysis of these fluids experimenters hope to measure body

hormones_ electrolytes_ proteins_ amino acids and enzymes which may be

produced as a result of stress.

2. Calcium Balance Study

The rate and amount of calcium change to the body during the con-

ditions of orbital flight will be evaluated in this experiment by means

of controlled calcium intake and output measurements. In addition to

calcium_ other electrolytes of interest such as nitrogen phosphorous_

sodium chloride and magnesiumwill be monitored.

The two astronauts will be maintained on a prescribed calcium diet

for two weeks prior to flight, during and after flight. Careful record-

ing of input-output will be accomplished and total fecal and urine

specimens will be preserved for analysis. Sweat will also be measured

by careful cleansing of the crew in distilled water following recovery.

Undergarments will be similarly cleaned and the water analysed.

3. In-Flight Sleep Anal_sis

The objectives of this experiment are to assess the astronauts'

state of alertness_ levels of consciousness, and depth of sleep during

-more-

-16

flight. An electroencephalograph (EEG) on the astronauts will be taken

daring weightless flight to establish the possible use of the EEG as a

monitoring tool to help determine the state of alertness and depth of

sleep. The electrical activity of the cerebral cortex will be monitored

by two pairs of scalp electrodes and recorded on the biomedical recorder.

4. Optical Communication (Laser)

Laser is an acronym for Light _Amplification by Stimulated Emission

of Radiation° Stimulated emission is produced by greatly exciting the

atom. When excited the atom will emit small quantities of light in

phase or unison. Thus the light is "coherent, " that is, it is directed

in a constant steady beam in one precise direction.

This experiment is an attempt to demonstrate a new technique for

communication between an orbiting spacecraft and a ground station. In

doing this, a demonstration of optical frequencies for communications

will be achieved and certain atmospheric data will be recorded and the

value of an astronaut as a "pointing control" will be established.

The primary atmospheric data to be obtained are background radiance

and attenuation. This data and the experience obtained from this experi-

ment will be useful in designing future systems.

The experiment equipment consists of a flight transmitter and a ground-

based receiver transmitter system.

The flight transmitter resembles and is about the same size as a home

movie camera. It weighs about six pounds and is completely self-contained.

It is made up of four injection lasers, a lO-volt power supply (eight

rechargeable nickel-cadmium batteries), a d.c. (direct current) to d.c.

converter, a telescopic sight and a microphone.

-more-

-17-

Four gallium arsenide injection lasers are the heart of the

transmitter. They deliver a total of 16 watts of light power at a

wavelength of 9,000 angstroms. The beams produced by the lasers form

four lines of light arranged one above the other making a square

pattern at distances of several feet to infinity.

Injection lasers were chosen for their compactness, light weight

and efficiency in converting electric energy into light energy.

The ground-based receiver resembles a short, blunt telescope. It

is 30 inches in diameter and consists of a collector and focusing unit

with a photomultiplier (optical detector) located at the focal plane.

An argon gas laser beacon is mounted atop the receiver barrel.

The argon gas laser has an output of three watts into a three milli-

radian beam spread or about 0.17 degree. At 300 miles the beam will be

approximately 0.9 mile in diameter.

Receiver systems have been installed at White Sands Missile Range_

Ascension Island and Kauai, Hawaii. The receivers are slaved to FPS

radars and always point toward the spacecraft when it is within range

of the radar.

In operation the command pilot will maintain proper spacecraft

orientation while the co-pilot aims the laser transmitter by sighting

through the telescope at the ground-based argon laser. The argon laser

beam will be visible to the naked eye.

When the spacecraft laser beacon is acquired by the ground receiver

the ground-based argon laser viii be flashed to indicate that contact

has been established. Both beacons will then be aligned and voice

-more-

communications can begin. The co-pilot will switch to the voice channel

and say, "i, 2, 3, 4, 5, testing 5, 4, 3, 2, 1."

Voice communications will be one way only - from spacecraft to ground.

During the experiment the astronauts will wear safety goggles for

protection against eye damage which might be caused by stray or reflect-

ed light from the onboard laser. The glasses have shields for stopping

radiation which enter the eye from the side and lenses that filter out

the infrared energy emitted by the laser.

5. Landmark Contrast Measurements

The purpose of this experiment is to measure the visual contrast of

land-sea boundaries and other types of terrain to be used as a service

of navigation data for the onboard Apollo Guidance and Navigation system.

Landmark contrast measurements made Ik'om outside the atmosphere will

provide data of a high confidence level to effectively duplicate naviga-

tion sightings for Apollo.

Landmark measurements _rlll be made of such areas as the Florida Coast_

South American Chilean Coast I African-.Atlantic Coast and A_stralian Coast.

A photometric telescope sensor and equiI_nent used for the Star Occulta-

tion Navigation experiment will be used.

6. Star Occultation Navigation

K_e feasibility and operational value of star occulting measurements

in the development of a simple, accurate and self-contained orbital

navigational capability will be investigated in this experiment.

The astronauts will determine the orbit of the Gemini spacecraft by

measuring the time stars dip behind an established horizon.

-_re -

-19-

As much of the existing Gemini onboard equipment as is possible will

be used for the recording of photometric sensor output signal intensity

and time. Nevertheless, certain special equipment will be necessary for

the performance of the navigational studies. Included in the equipment

is a photoelectric sensor.

The photoelectric sensor consists of a telescope, eyepiece, reticle,

partially silvered mirror, iris, chopper, optical filters, photomulti-

plle_, pre-amplifier and associated electronics. The instrument is

hand-held to the astronaut's eye for viewing out the spacecraft's

window.

Asthe astronaut views the horizon, he looks for bright stars about

to be occulted. He then points the telescope at one and centers the

star within a reticle circle. A portion of the radiation is then

diverted to a photomultipliero With a hand-held switch, the astronaut

initiates a calibration mode in which the intensity of the star is

measured automatically° }_ then tracks the star within the reticle as

the star passes into the atmosphere and behind the edge of the earth.

The tracking period for each star is approximately lO0 seconds. During

this tracking period the astronaut will manually indicate the passage

of the star through the air glow, the 50% intensity level and complete

occultation simply by momentarily depressing the calibration switch.

The astronaut plays an essential role in the procedure, First, he

solves the star acquisition problem by locating the next star to be

transited. Second, he uses his head to point the telescope thus elimin-

ating a two-gimbal automatic tracking system which would of necessity

be used if he were not onboard. Third, he records star occultation times

-NK)re-

-20-

manually for comparison with the automatic calibration mode. Finally,

he notes peculiarities in the data as it is collected. In performing

this latter function_ the man is used to greatest advantage to advance

the state of the navigational art as rapidly as possible.

-21-

CAME_ EQUIPMENT FOR G_MINI 7 AND 6 MISSIONS

16_94MAURER MOVIE CAMERA

I. Camera

A. Equipment

i. two cameras

2. 75mmlens (one camera)3. 75ram,25ram,18ramlens set (second camera)

B. Characteristics

1. Six frames/second2. f-ll aperture3. 1/200 second shutter speed4. 40 lines/mmresolution

II. FiLm

Kodak S. O. 217 color film

III. purpose

Weather and Terrain PhotographyGeneral purpose

-more-

I

-22-

70MM HASSELBLAD CAMERA

I. Camera

A. Equil_nent

1. Camera2. 80mm lens3 • 250nmmlens4. Photo event indicator

5. Ring Sight6. UV filter7. Film backs

B. Characteristics

1. 80_n focal length2. f2.8 to f22.0 aperture

3. Time exposures and speeds up to 1/500 second4. Resolution: approximately 125 lines/mm5. Approximately 1.5X magnification

II. Film

Kodak S. O. 217, MS, EktachromeASA-64 color emulsion on 2.5 railEstar Polyester base

III. Purpose

Weather and TerrainGeneral Purpose

-more-

-23-

G_IINI 7

FOURTEEN DAY P_NU CYCLE

MENU I - DAYS i. 5. 9 & 13 _NU ii - DAYS 2,6, i0 & 14

MEAL A Days 5, 9, 13 only CALORIES MEAL A CALORIES

(R) Grapefruit drink 83 (R) Grapefruit drink 83(B) Apricot cereal cubes (8) 114 (R) Chicken end gravy 9_(a) Sausage patties (2) 223 (B) Beef sandwiches (6) 268(R) Banana pudding 282 (R) Applesauce 165(R) Fruit cocktail 87 (B) Peanut cubes (6) 297

Al_ricot cereal cubes (day 13 only_°9_905

MEAL B M_AL B

(R_ Beef and vegetables 98 (_) Orange-grapefruit 83(_) Potato salad 1Z_3 (R) Beef pot roast 119(B) Cheese sandwiches (6) 324 (B) Bacon & egg bites (6) 206(B) Strawberry cubes (6) 283 (2) Chocolate pudding 307(R) Grange drink 83 715

931

MEAL C

_AL C Days 2, 6, iO only(R) Orange-grapefruit drink 83(R) Tuna salad 214 (R) Potato soup 220(R) Apricot pudding 150 (R) Shrimp cocktail 119(B) Date fruitcake (4) 262 (B) Date fruitcake (4) 262

709 (R) Orange drink 8)684

Total Calories 2,429Food 0nlyWeight 521.12 gm Total Calories 2,304

Food 0nly Weight 518.62 gm

(B) = Bite-sized food not requiring rehydration prior to ingestion.Usual serving consists of six bite-sizepieces.

(R) = Rehydratable food, i.e., food which must be reconstituted priorto ingestion.

-more-

MENU III- Day 3, 7, ll MENU IV - Day 4, 8, 12

M_AL A CALORZES _AL A CALORIES

(R) _a]_lon_alad 2A6 (B) Strawberry cereal(R) Green peas 81 cubes (8)-day 8 only ll4(B) Toasted bread cubes (8) 1O7 (B) Bacon squares (4) 135(B) Gingerbread (6) 183 (R) Ham and applessuce 127(_{) Cocos 190 (R) Chocolate pudding 307

Toasted bread cubes - day 3 807 (R) Orange drink 82only 766

_AL BMEAL B

(R) Grapefruit drink 83(B) Bacon squares (4) 90 (R) Beef and gravy 16C(_) Chicken & vegetables 75 (R) Corn chowder 252(B) Apricot cubes (6) 284 (B) Brownies (6) 2A1(B) Pineapple fruitcake (6) _79 (_) Peaches __

911 751

M_AL C I_AL C

70 (B) Coconut cubes (6) 310(B) Cheese sandwich (6) 324 (B) Cinnamon to_st (6) 99(g) Butterscotch pudding 234 (S) Chicken salad 237(R) Orange drink 8_ (S) Applesauce 165

711 (_) Grepefrut drink 83894

Total Calories 2,&29Food Only Weight 515.06 gm Total Calories 2,All

Food Only Weight 509.58 gm

-monte -

-25-

G_INI 6 LAUNCH PREPARATIONS

The launching of Gemini 7 and the rapid turn-around for the Gemini 6

mission will be one of the most complex operations ever conducted by launch

operations crews. A work schedule has been established for

flight testing, checkout and launching of Gemini 6 nine days after

Gemini 7.

The Gemini 6 spacecraft and launch vehicle were checked out

thoroughly and counted down to some 42 minutes before liftoff on

October 25. Since that time both the spacecraft end launch vehicle

were placed in "bonded" storage under guard to insure that their

mechanical and electrical integrity remains intact.

The Gemini 6 checkout will be the same as if a problem had

occurred several days before the originally planned Gemini 6 flight

and the spacecraft had to be de-mated from the launch vehicle. With

the problem solved, the spacecraft would again be _mted and a "compressed"

checkout would take place in the days leading up to a launch, as most

of the previous testing was still valid.

Once Gemini 7 has been launched_ crews will be ready to erect

the 6 launch vehicle and mate the spacecraft as soon as possible. The

schedule calls for this to be completed some 24 hours after Gemini 7

liftoff.

Certain testa conducted during a normal mission will not have

to be repeated for Gemini 6 because they will still remain valid

(their validity will be checked, however). These include various

calibrations of launch vehicle, spacecraft and blockhouse automatic

•,-mo_e -

-26-

ground support equipment; weight and balancing of the erector,

certain spacecraft pre-mate and extensive spacecraft launch vehicle

combined systems tests. Another departure from regular checkout

procedure is that the Gemini 6 spacecraft will be fueled and the

water supply and batteries will be installed before it gets to the

launch pad.

The spacecraft and launch vehicle crews (McDonnell Aircraft is

prime contractor for the spacecraft and Martin Company for the

launch vehicle) will work on a three-s_ft, 24_hour schedule during

the period between the launches.

The following is a general outline of the comprehensive work

schedule:

The Gemini 7 is scheduled for launch at 2:30 p.m. EST.

As soon as possible an assessment of pad damage will be made.

The blast d_ge has been very minimal in the past, requiring replace-

meritpri_rily of some expendable wiring at the base of the pad.

Various umbilical cables etc. will be checked to insure that they

are operating. This work can be accomplished at the same time as

the two launch vehicle stages are being erected end as the spacecraft

is mated.

During launch days plus one and two_ preparations will be made

for final spacecraft systems tests. The validity of the electrical

interface between the spacecraft and launch vehicle _ill be verified

on the third day as individual tests of the two continue.

-more-

-27-

The final spacecraft systems tests are to be conducted on days

three and four. During this time the previous verification of

guidance betwe_ the spacecraft and launch vehicle is checked.

Liquid oxygen for the spacecraft environmental control system

will be loaded aboard during this time as preparations are made for

the simulated flight, scheduled for launch day plus five. From this

point, to Gemini 6 liftoff, the checkout will be generally the saae

as of any other Gemini flight.

The simulated flight, which lasts some i0 to 12 hours, consists

of three simulated launches -- A mode II abort run (an abort occurs

some 1:38 after liftoff), a switchover to secondary guidance during

powered flight, and finally, a normal flight and insertion into

orbit, during which various orbital exercises, reentry and recovery

tests are run. The prime pilots and their backups participate in

these tests aboard the spacecraft at Launch Complex 19.

Another "time saver" comes after the simulated flight when the

various pyrotechnics aboard the spacecraft ere thoroughly checked

and connected. Since the pyrotechnics system was varified previously

and left in a flight mode configuration, only a short test for verifi-

cation will be required.

The Gemini 6 pre-_ount (lasting some four hours on the third day before

launch) and the mid-count (lasting some four hours on the second day before

launch) will be very s_m_lar to regular Gemini procedures. During the pre-

count significant portions of each spacecraft system ere again checked.

-__0 i_e -

-28-

Final interface tests between the spacecraft and launch vehicle

(guidance, abort procedures etc.) are conducted during the mid-count.

The Gemini 7 and 6 final countdowns will be about the same--

the spacecraft starting at about T-6 hours end the launch vehicle

at T-4 hours. However, on Gemini 6, s hold will be declared st T-3

minute mark in the count to adjust the launch time to the planned

rendezvous with Gemini 7. This hold will last 25 minutes. The

Gemini 6 launch time is scheduled for 9:35 a.m. EST.

-more.-

-_{9-

LAUNCH VEHICLE COUI_£DOWN

Gemini 6

F-3 days Start pre-count

F-1 day Start mid-count

T-12 hours GLVpropellant loading

T-390 minutes Complete propellant loading

T-3OOminutes Begin terminal countdown

T-120 minutes K[ight Crew to Complex 19

T-9O minutes Crew enters spacecraft

T-75 minutes Close spacecraft hatches

T-50 minutes White Room evacuation

T-35 minutes Begin erector lowering

T-15 minutes Spacecraft OAMS static firing

T-3 minutes 25-minute hold

T-04 seconds GLVignition

T-O seconds Liftoff

T+2 minutes_ 36 seconds Booster engine cutoff (BECO)

T+5:41 Second stage engine cutoff (SECO)

T+6:II Spacecraft-launch vehicle separation

-mo re-

-30-

NOMINAL MISSION PLAN

Gemini 6

Gemini 6 is scheduled to be launched December 13 at shout 9:34am EST

from Launch Complex 19 at Cape Kennedy, Fla. It will be launched into

an elliptical orbit of 168 miles apogee and lO0 miles perigee. Second

stage booster yaw steering will be used to place the spacecraft into the

same orbital plane as Gemini 7. Yaw steering provides up to 0.55 degree

inclination increment change if needed. The spacecraft will trail Gemini 7

by 1208 miles at insertion.

Launch Windows (EST)

Nominal Day 9:34am to lO:21am ll:O_am to ll:24am

N + 1 9:38am to lO:25am

N + 2 8:07s_ to 8:54am 9:42am to lO:14am

N + 3 8:llam to 8:51_m

N + 4 6:59am to 7:25am 8:14am to 9:01am

Rendezvous is planned for the fourth orbit of Gemini 6, if liftoff

is on time. During the first 35 minutes of each launch opportunity each

lO0 seconds delay in liftoff delays rendezvous by one spacecraft orbit.

If liftoff time occurs beyond 300 seconds, rendezvous will not be

attempted until the beginning of the seeonc_ day when better tracking

coverage is available.

Sho_h]. l[ftoff occur clurin_ the last 12 _minutes oI.'the r_×imum

47 minute win_Jow, a different intermediate sequence of maneuvers will

be initiated to narrow the catch-up distance between the spacecraft.

-more-

-31-

In this case, engine cutoff occurs earlier to reduce velocity by

50 feet per second. This causes the spacecraft to be inserted into

a lower orbit than planned, with a perigee of about i00 miles and

apogee of 138 miles. In this orbit the Gemini 6 catchup rate will

be increased due to the greater difference in altitude between the

two spacecraft.

Varying insertion velocity as described above has the effect

of widening the launch window.

Following a successful, on-tlme liftoff and insertion the

uncertainties of the effect of drag on the spacecraft during its

initial orbit may require a one foot per second posigrade burn at

first perigee to raise apogee. In the event of small insertion

dispersions, the magnitude of this maneuver may vary but the result-

ing apogee will be 168 miles.

Near the second apogee a posigrade burn will add 53 feet per

second to raise perigee to about 134 miles. This reduces the catchup

rate from 6.7 degrees to 4.5 degrees per orbit and will provide the

proper phase relationship between the two spacecraft for circulari-

zation at third apogee.

Should the two spacecraft be in different planes, s plane adjust-

ment will be made by Gem/ni 6 at the common node (where the two space-

craft orbits intersect) following the second apogee posigrade burn.

At the third Gemini 6 spacecraft apogee, a posigrade burn of 53

feet per second will be made to circularise the orbit at 146 miles.

-more-

_3L)_

-33-

Gemini 6 will then be trailing Gemini 7 by about 184 miles.

This is within range of the onboard radar and lock-on should have

occurred.

A 32 feet per second posigrade burn will be made at terminal

phase initiation along the line of sight to Gemini 7. This will be

at a ground elapsed time of about 5 hours, 15 minutes - about one

minute after entering darkness. The range between the spacecraft

at this time is expected to be about 39 miles.

Approximately 33 minutes following terra,el phase initiation

a posigrade velocity of 43 feet per second will be applied to

Gemini 6. This places the two spacecraft into the same orbit and

rendezvous will have been accomplished.

Should there be ccuputer, platform or radar failure, the mission

can still proceed using ground data and radar-optical or optical

rendezvous modes.

Retrofire will occur at a ground elapsed t_m_ of 46 hours and

I0 minutes, during the 29th revolution. Landing will be in the

West Atlantic recovery area.

-more-

-35-

G_NI 6 EXPEi_NTS

Three experin_nts will be performed during the Gemini 6 mission:

i. Synoptic Weather Photography

2. Synoptic Terrain Photography

3. _adiation in sImcecraft

The photogrsphy experiments are repe_ts of those flown on

all previous Gemini flights. A description of these eppears in

the Gemini 7 experiments section.

The radiation experiment is designed to n_asure r_di_tion

levels and distribution inside the spacecraft. 3even sensors are

located throughout the spacecraft. One is shielded to simulate

the amount of radiation the crew members 8re receiving beneath their

skin. The shield w_ll be removed as the spececraft p2sses through

the South Atlantic anomaly, the area where the radiation belt

dips closest to the earth's surface.

This experiment was _iso flown on Gemini 4.

-36-

DAy #I MEAL "A" CALORIES

Bacon Square 90Potato Soup (Rehydratable) 252Gingerbread 183Peanut Cubes 297Grapefruit Drink (Rehydratable) 83

TOTAL CALORIES

MEAL "B"

Chicken and Gravy (Rehydratable) 92Cheese Sandwiches 324Strawberry Cereal Cubes 171Pineapple Fruitcake 2530range-Grapefruit Drink (Rehydratab2e) 83

TOTAL CALORIES

MEAL "C"

Salmon Salad (Rehydratable) 21_6Cinnamon Toast 99Butterscotch Pudding (Rehydratable) ii?Brownies 241

Grapefruit Drink (Rehydratable) 83TOTAL CALORIES -_

FIRST DAY - TOTAL 2,611_

-more-

-37-

DAY #2 MEAL "A" CALORIES

Chicken Sandwich 196Shrimp Cocktail (Rehydratable) i19Date Fruitcake 262Coconut Cubes 310

0range-Grapefruit Drink (Rehydratable) 83TOTAL CALORIES --97-0---

MEAL "B"

Tuna Salad (Rehydratable) 214Apricot Cereal Cubes 171Strawberry Cubes 283Peaches (Rehydratable) 98Grapefruit Drink (Rehydratable) 83

TOTAL, CALORIES

MEAL "C"

Bacon and Egg Bites 178Meat & Spaghetti (Rehydratable) 70Toasted Bread Cubes 161

Chocolate Pudding (Rehydratable) 307Grapefruit Drink (Rehydratable) 83

TOTAL CALORIES

SECOND DAY TOTAL 2,618

-more -

-38-

MANNED SPACE FLIGIIT NEw'WORK

G_41NI 7AND 6 MISSIONS

The Manned Space Flight Network consists of NASA and Delm_rtment of

Defense facilities.

1_e Mission Control Center in Houston, Texas (MCC-H) will control

the entire Gemini 7-6 mission. As on Gemini _missions 4 and 5, Houston's

Real-Time Computer Complex (RTCC) (a key element of the MCC-H) will serve

as the mission computing center.

For Gemini 7-6 the network will provide:

(i) Tracking and telemetry data during launch and orbital phases

from both the Gemini 7 and the Gemini 6 spacecraft for position determination

and systems operation.

(2) Capability for transmission and verification of ground commands

to either or both spacecraft. These commands s generated at the mission

control center s update the spacecraft computer to provide ctu_rent infor-

mation for time-of-retrofire determination and reentry calculations and

di splays.

Prime Computin_ Su_ort

Immediate computing support will be provided from launch through

impact by the RTCC at the Manned Spacecraft Center. During the launch

and insertion phase s the RTCC will receive high-speed radar data from

Bermuda and radar and MISTRAM (Missile Tracking and Measurement System)

data from the Air Force Eastern Test Range (AFETR) radars via the Cape

Kennedy-Houston GLDS (Gemini Launch Data System).

Other Computer Support

NASA's Goddard Space Flight Center (GSFC) real-time computing support

for Gemini 7-6 includes the processing of skin tracking information

-more-

-39-

obtained from the second stages of both launch vehicles and the

computation of their predicted impact points. Additionally_ the

GSFC RTCC will generate skin track (radar echo bounce) space

position predictions for the Manned Space Flight Network and the

Department of Defense for their use in the event of spacecraft

beacon loss or powered-down flight.

Network Readiness

Computers at the GSFC will certify the worldwide network's

readiness to support Gemini 7-6 through a system-by-system TLM,

CMD_ RDR_ station-by-station_ computer-progrsmmed checkout method

called CADFISS (Computation and Data Flow Integrated Subsystem Tests).

Checkout of network facilities also _ll be performed by the GSFC

_ring post-launch periods when the spacecraft are not electronically

"visible" by some stations and continue until the vehicles are again

within acquisition range.

Data Flow Tests (DFT's) from the worldwide network to the Manned

Spacecraft Center's Real-Time Computing Complex will be conducted from

the Manned Spacecraft Center under the direction of the CADFISS Test

Director.

TRACKING TWO MANNED SPACECRAFT

For Gemini 7-6, various combinations of spacecraft trackln_ and

data acquisition assignments will be accomplished according to individual

station capability.

-more-

-40-

Both Gemini spacecraft are equipped with C-Band beacon systems

that aid station radars of the Manned Space Flight Network in pin-

pointing precise space position of each vehicle. In order that these

radiated signals be readily distinguishable by the ground systems,

their identifying codes have been altered slightly for precise

recognition.

Through the detection of the spacecraft beacon, ground trackers

pinpoint each spacecraft with an accuracy equivalent to a 22 bullet

hitting a twenty-five cent piece at a distance of one mile. Electroni-

cally coordinated (slaved) telemetry receiving and radio command

antenna systems acquire data from and send instructions to each

spacecraft based in part on the space position information provided

by the beacon tracking radars.

After Gemini 6 spacecraft insertion into orbit, stations in the

Manned Space Flight Network will, for the first time, simultaneously

track and acquire information from two orbiting manned spacecraft.

While both spacecraft are in orbital flight the on-slte flight

data summary computer: (UNIVAC 1218) called TOMCAT (Telemetry 0n-Line

Monitoring_ Compression and Transmission) processes Gemini 6 or 7

(whichever spacecraft has been designated "prime") spacecraft data.

Upon termination of the Gemini 6 mission, all network station

systems will revert to previous Gemini 7 operating modes for the

remainder of the mission.

-more-

-41-

ORBIT3 - _OLU'i'lON_

The sp_cecrsft's course is messured in revolutions eround the

earth. A revolution is completed esch time the sp_cecrsft pssses

over 80 degrees west longitude, or at Gemini sltitudes sbout once

every 96 _inutes.

Orbits are spsce referenced and in Gemini tske _bcut 90 minutes.

-moPe-

-21.2-

CREW TRAINING BACKGROUND

In addition to the extensive general training received prior to

flight assignment the following preparations have or will be accom-

plished prior to launch:

1. Launch abort training in the Gemini Mission Simulator and the

Dynamic Crew Procedures Simulator.

2. Egress and recovery activities using a spacecraft boilerplate

model and actual recovery equipment and personnel, pad emergency

egress training usin_ elevator and slide _rlre.

3. Celestial pattern recognition in the Moorehead Planetarium,

Chapel Hill, North Carolina.

4. Parachute descent training over _ater using a towed parachute

technique.

5. Zero gravity training in KC-135 aircraft.

6. Suit_ seat and harness fittings.

7. Training sessions for each crew.

member on the Gemini translation and docking simulator.

9. Detailed systems briefing; detailed experiment briefings; flight

plans and mission rules reviews.

IO. Participation in mockup reviewsj systems revie_ subsystem tests

and spacecraft acceptance review.

-more-

-43-

During final preparation for flight, the crew participates in

network launch abort simulations, Joint combined systems test and

the final simulated flight tests. At T-two days, the major flight

crew medical examinations will be administered to confirm readiness

for flight and obtain data for comparison with post-flight medical

examination results.

-more-

-44-

IMMEDIATE PEE-FLIGHT CREW ACTIVITIES

T-7 hours Back-up flight crew reportstc the 100-foot level of the

White Room to participate infinal flight preparations.

T-5 hours Pilots' ready room, lO0-footlevel of White Room and crew

quarters manned and made readyfor prime crew.

T-% hours, 30 minutes Primery crew awekened

T-4 hours Medical examination

T-_ hours, &O _dnutes Breakfast

T-3 hours, 15 minutes Crew leaves euarters

T-3 hours, 5 minutes Crew arrives st ready roomon Pad 16

During the next hour, the biomedical sensors are placed, under-

wear end signal conditioners are donned, flight suits minus helmets

and gloves are put on end blood pressure is checked. The helmets

and gloves are then etteched and con_unications end oral temperatures

systems are checked.

T-2 hours, 15 minutes Purging of suit begins

T-2 hours, 4 minutes Crew leaves reedy room

T-2 hours Crew arrives _t lO0-footlevel

T-I hour, 30 minutes Crew enters spacecraft

From entry until ignition, the crew participetes in or monitors

systems checks and preparations.

-more-

-_5-

_t Activities

At ignition the crew begins the primary leunch phase task of

assessing system status end detecting abort sittmtions. Thirty

seconds after _Co, the co_snd pilot initietes forwerd thrusting

and the pilot actuates spacecraft separetion end selects rate

contend attitude control. Ground ccmput_,tions of insertion velccity

corrections are received end velocity adjustments ere m_de by forwerd

or aft thrusting. After successful insertion and completion of the

insertion check llst, the detailed flight plan is begun.

-46-

CREW SAFETY

Every Gemini system affecting crew safety has a reduadant

(Back-up) feature. The Malfunction Deteetion System aboard

the launch vehicle monitors subsystem performance and warns

the crew of a potentially catastrophic malfunction in time

for escape.

There are three modes of escape:

MODE I Ejection seats, and personal parachutes,used at ground level and during first50 seconds of powered flight, or duringdeseent after reentry.

MODE II (Delayed) Retrorockets used between 50 and i00seconds, allowing crew to salvo fire allfour solid retrorockets five seconds

after engine shutdown is cow,handed.

MODE III Normal separation from launch vehicle,using OAMS thrusters, then makingnormal reentry, using computer.

Except for Mode I, spacecraft separates from Gemini Launch

Vehicle, turns blunt-end forward, then completes reentry and

landing with crew aboard.

Survival package

Survival gear, mounted on each ejection seat and attached

to the astronaut's parachute harnesses by nylon llne, weighs

23 pounds.

- more -

-47-

Each astronaut has:

3.5 pounds of drinking water

Machete

0ne-man life raft, 5½ by 3 feet, with CO 2 bottle for in-

flation, sea anchor, dye markers, nylon sun bonnet.

Survival light (strobe), with flashlight, signal mirror,

compass, sewing kit, 14 feet of nylon line, cotton balls and

striker, halazone tablets, a whistle, and batteries for power.

Survival radio, with homing beacon and voice reception.

Sunglasses.

Desalter kit, with brickettes enough to desalt eight pints

of seawater.

Medical kit, containing stimulant, pain, motion sickness

and antibiotic tablets and aspirin, plus injectors for pain and

motion sickness.

-more-

- 8-

G_MINI 6 SUIT

The pressure suit worn by the crew of Gemini 6 is identical

to that worn by the Gemini 5 crew. It is not suitable for extra-

vehicular activity.

It has five layers:

1. White cotton constant wear undergarment with pocketsto hold biomedical instrumentation equipment.

2. Blue nylon comfort layer.

3. Black neoprene-coated nylon pressure garment.

4. Restraint layer of dacron and teflon link net torestrain pressure garment and maintain its shape.

5. White HT-lnylon outer layer to protect against wearand solar reflectance.

The suit is a f,ll pressure garment, including a helmet_rlth

mechanically sealed visor. Oxygen is furnished by the environmental

control system. Gaseous oxygen is provided to the suit through a

"suit loop" to cool the astronaut and provide him_rith a breathable

atmosphere of i00 percent oxygen. Oxygen in the cabin maintains 5.1

pounds per square inch (psi) pressure. The suit_ if cabin pressure fails,

is pressurized to 3.5 psi (+.4,-0).

-more -

-49-

G_L_[INI7 SUIT

A new lightweight suit has been developed for long duration

space flights. It will be worn for the first time by the Gemini 7

crew. it is en intravehicular suit desigmed to give maxim_un

_Jbility when depressurized.

It has two layers:

i. The inner layer is the pressure retaining neoprene-

coated nylon bladder.

2. Th_ outer layer is six ounce HT-I nylon

it is a full pressure suit and weighs 16 pounds, including

an aviator's crash he]]net which is worn under the soft helmet.

The suit can be completely taken off during flight or c_n be worn

in a partially doffed mode in which gloves and boots are removed

and the helmet is unzipped at the neck and rolled back t(Jform a

headrest.

.Exael'gencyti,,_eto donn the suit from a p_rtielly doffed mode

is about _) seconds. When the suit is totally doffed it takes from

five to ten minutes to donn it.

-50-

MEDICALCHECKS

At least one medical check a day will be made by each crew

member. Performed over a convenient ground station, a check will

consist of: Oral temperature# blood pressure measurement_ food

and water intake evaluation.

BODY WASTE DISPOSAL

Two separate systems are used for collection of body wastes.

A plastic bag with an adhesive lip to provide secure attach-

ment to the body is used for the collection of feces. It contains

a germicide which prevents formation of bacteria and gas. Soiled

itemsj toilet tissues and a wet towel_ are placed in the bag

following use. The adhesive lip is then used to form a liquid seal

and the bag is rolled and stowed in the empty food container spaces

and brought back to earth for analysis.

Urine is collected into a horn-shaped receptacle with a self

adjusting opening. The receptacle is connected by a hose to a

pump device which either transfers the liquid to the evaporator

or dumps it overboard. The system is much like the relief tube used

in military fighter planes.

FOOD

Number of Meals -- Three per day per astronaut°

Type -- Bite-sized and rehydratable. Water is placed in

rehydratables with special gun. Bite-sized items need no rehydration.

-more-.

-51-

Storage-- Meals individually wrapped in aluminum foil and

polyethelene_ polyamide laminate. First day meals stored in

compartment beside knees of each crewman. Succeeding days meals

in right aft food compartment.

The water intake of each astronaut will be carefully measured.

A mechanical measuri_ system is an integral part of the water

gun. It consists of a neoprene bellows housed in a small metal

cylinder mounted at base of gun. The bellows holds one-half

ounce of water. When plunger of gun is depressed_ a spring

pushes water out of bellows and through gun. A counter in right

side of gun registers number of times bellows is activated. Each

crewman will record how much he drinks by noting numbers at

beginning and end of use of gun_

-more-

-52-

The following are guidelines only, Conditions along the grotmd

track will be evaluated prier to and during the mission.

Launch Area

Surface Winds -- 18 knots with gusts to 25 knots

Ceiling -- 5,000 feet cloud base

Visibility -- Six miles

Wave Height -- Five feet maximum

Planned I_udin_ Ar_

Surface Winds ~- 30 knots maximum

Ceiling -- 1,500 feet cloud base

Visibility -- Six miles

Wave Height _ Eight feet maximum

Contineenc_ Landin_ Areas

Fllght director will make decision based upon conditions at the

time.

Parare_cue_

Surface Winds -- 25 knots maximum

Ceiling -- ipO00 feet cloud base

Visibility -- Target visible

Waves -- Five feet maximum; swells I0 or ii feet maximum

-illo32e -

-53-

PLANNF_ AND CONTINGENCY LAN_ING AREAS

There are two types of landing areas for Gemini spacecraft,

planned and contingency. Planned areas are those where recovery

forces are pre-positioned to recover spacecraft and crew within a

short time. All other areas under the orbital track are contingency

areas, requiring special search and rescue techniques and a longer

recovery period.

P_a_ne_ Lan_ing Area_

PRIMARY Landing in the West Atlantic where theprimary recovery vessel, an aircraftcarrier, is pre-positioned.

S_CON_ARY Landing in East Atlantic, West Pacificand Mid-Pacific areas where ships aredeployed.

LAUNCH SITE Landing in the event of off-the-padabort for abort during early phase offlight, includes an area about 41miles seaward from Cape Kennedy, 3miles toward Banana River from Complex 19.

LAUNCH ABORT Landing in the event of abort duringpowered flight, extending from 41 milesat sea from Cape Kennedy to west coastof Africa.

Contingency Landin_ Areas

All the area beneath the spacecraft's ground track except those

designated Planned Landing Areas are Contingency Landing Areas, roquir-

ing aircraft and pararescue support for recovery within a period of

18 hours from splashdown.

Recovery forces will be provided by the military services, and

during mission time will be under the operational control of the

Department of Defense Manager for Manned Space Flight Support Operations.

-more-

OEMINI SPACgCRAF I'

The Gemini spacecraft is conical, 18 feet, 5 inches long, lO feet

in diameter at its base and 39 inches in dia_.eter at the top. lts

two major sections are the reentry module and the adapter section.

_eentry _odule

The reentry module is ii feet high and 7_ feet in diameter ,t its

base. It has three main sections: (I) rendezvous and recovery (_R),

(k) reentry control (_iCS), and (3) cabin.

_ndezvous and recovery section is the forward (small) end of the

spacecraft, containing drogue, pilot and main p_rachutes and radar.

_eentry control section between _&_ and cabin sections contains

fuel and oxidizer tanks, valves, tubing and two rings of eight _ttJtude

control thrusters each for control during reentry. A parachute ad_pter

assembly is included for main parachute attachment.

Cabin section between RCS and adapter section, houses the crew

seated side-by-side, their instruments and controls. Above each se_t

is a hatch. Crew compartment is a pressurized titanium hull. Equipment

not requiring pressurized environment is located between pressure hull

and outer beryllium shell which is corrugated and shingled to provide

aerodynamic and heat protection. Dish-shaped heat shield forms the

large end of cabin section.

Adapte.r _ection

The adapter section is 7_ feet high and i_ feet Jn diameter at Jts

base, containing retrograde and equipment sectJ ons.

-i_ore -

-56-

1.1.1

:DI--!

I--

O

O _ >-

O D

c,D I---I.U

zOO__Z,,,O

I--

<I: 0 -r_:_ UUI.U a.U

-57-

t_

0Zm

C_I,LI

..... ,, ,, ,,,,,, •

-£;8-

". /

-59-

.Retrograde section contains four solid retrograde rockets and

part of the radiator for the cooling system.

Equ_pmentse_c_io_nn contains electrics1 power source systems, fuel

for the orbit attitude and _mnuever system (OA_S), primary oxygen for

the envlron_entsl control system (ECS). It also serves as a radiator

for the cooling system, also contained in the equipment section.

NOTE: The equipzJ_nt section is jettisoned immediately before

retrorockets are fired for reentry. The retrograde section is jettisoned

after retros are fired.

P_OPELLANT

Gemini-? -- &23 pounds

Gemlni-6 -- 669 pounds

GEMINI -7 SPACEC_A_!MODIFICATIONS

The following modifications have been made to the Gemini-? sp_ce-

craft to support Gemini-6 rendezvous mission:

1. A transponder to receive end transmit signals from the Gemini-6

rendezvous radar system has been installed in the nose of the spacecraft.

2. Two acqusition lights have been placed on the adapter section

180 degrees aport. These are the same lights designed for the Agena

target vehicle. They flash about 80 times per minute and can be seen

for approximately 23 _iles.

P_NDEZVOUS RADA_

Gemini-6

Purpose -- _ables crew to measure range, range rate, and bearing

angle to Ge_inl-7. Supplies data to Inertial Guidance System computer

-_ore-

-60-

so crew can determine maneuvers necessary for rendezvous.

Operation -- Transponder on Gemini 7 receives radar impulses and

returns them to Gemini 6 at a specific frequency and pulse width.

Radar accepts only signals processed by transponder.

Location -- small end of spacecraft on forward face of rendezvous

and recovery section.

Size -- less than two cubic feet.

Weight -- less than 50 pounds.

Power Requirement -- less than 80 watts.

_L_CTRICAL POWER SYSTemS

Gemini-7

The fuel cell power subsystem includes two 68-pound pressurized

fuel cell sections, each containing three fuel cell stacks of 32 series-

connected cells. Operating together, these sections produce up to two

kilowatts of DC power at peak load.

Four conventional silver zinc batteries provide bBckuppower to

the fuel cells during launch and are l_ri_ power for reentry, landing

and post-landing. Three additional batteries are isoleted electricelly

to activate pyrotechnicsaboard the spacecraft. (The four m_in batteries

can also be brought on line for this purpose if necessary.)

Besides its two cylindrical sections, the fuel cell battery subsystem

includes a reactant supply of hydrogen and oxygen, stored ,t supercritlc_]

pressures and cryogenic temperatures.

-61-

'_rlergyis produced in the fuel ce]l by forc_g the reactants into

the stacks whore they ere chez,icslly changed by en electrolyte of

poly_er plastic end s catalyst of platin_, i_su]t_",t electrons end

ions combine with oxygen to form electricity, heaC end w_ter. This

chemic_l reaction will theoretically continue ss long es fuel end

oxid8nt are supplied. Electrici_y is used for power, heat is rejected

by the spacecraft coolant system, end w8ter is diverted into the

spacecraft drinking supply _anks where it is sepereted front the crew's

drinking supply by a bledder end used as pressursnt to supply drinking

water.

_emini-6

Gen_ni-6 spacecraft carries lO batteries. Included in these are:

Adepter Batteries three /_uO-emp/hour units, housed inthe adapter section. Primery powersource.

_ain Batteries four LS-amp/hour units in the reentry

section for power prior to end during

reentry.

_quib Batteries three 15-sJJlp/hour units in the r_entry

section, used to trigger e_plos]ve

squibs.

--mC r_]-

8

-64-

GI_LINI LAUNCH VEHICLE

The Gemini Launch Vehicle (GLV) is a modified U. S. Air Force Titan

II intercontinental ballistic missile consisting of two stages.

GLV dimensions are:

First Sta_e Second Sta_eF_IGHT 63 feet _ feet

DIAMET_q l0 feet lO feet

THRUST 430,000 pounds lO0,000 pounds(two engines) (one engine)

FUEL 50-50 blend of monomethyl hydrazlne and

unsymmet rical-dimethyl hydrazine

OXIDIZER Nitrogen tetroxide

(Fuel is hypergolic, ignites spontan-

eously upon contact with oxidizer).

Overall height of launch vehicle and spacecraft is 109 feet.

Combined weight is about 340,000 pounds.

Modifications to Titan II for use as the Gemini Launch Vehicle

include :

i. Malfunction detection system added to detect and transmit

booster performance information to the crew.

2. Backup flight control system added to provide a secondary

system if primary system fails.

3. Radio guidance substituted for inertial guidance.

4. Retro and vernier rockets deleted.

5. New second stage equipment truss added.

6. New second stage forward oxidizer skirt assembly added°

7. Trajectory tracking requirements simplified.

8. Electrical_ hydraulic and instrument systems modified.

-more-

-65-

Gemini Launch Vehicle program management for NASA is under the

direction of the Space Systems Division of the Air Force Systems

CoN_and.

-more-

, J

-66-

CREW BIOGRAPHIES

Frank Borman, Gemini 7 command pilot

BORN: Gary, Ind., Mar. 14, 1928

HEIGHT: 5 feet, I0 inches WEIGHT: 163 ibs. Blonde hair,blue eyes

EDUCATION: Bachelor of Science degree, United States MilitaryAcademy, 1950; Master of Science degree in aero-nautical engineering, California Institute ofTechnology, 1957.

MARITAL STATUS: Married to the former Susan Bugbee of Tucson,Ariz.

CHILDREN: Frederick, Oct. 4, 1951; Edwin, July 20, 1953

EXPERIENCE: Upon graduation from West Point, Borman, now anAir Force Major, chose an Air Force career and received hispilot training at Williams Air Force Base, Calif.

From 1951 to 1956 he served with fighter squadrons in theUnited States and in the Philippines and was an instructorat the Air Force Fighter Weapons School.

From 1957 to 1960 he was an instructor of thermodynamics andfluid mechanics at the U.S. Military Academy.

_ was graduated from the USAF Aerospace Research Pilots Schoolin 1960 and later served there as an instructor. In this capa-city he prepared and delivered academic lectures and simulatorbriefings, and flight test briefings on the theory and practiceof spacecraft testing.

Borman has logged more than 4,400 hours flying time, includingmore than 3,600 hours in Jet aircraft.

CURRENT ASSIGNMENT: Borman was one of the nine astronauts namedby NASA in September 1962.

Bo_nan is the son of Mr. and Mrs. Edwin Borman, Phoenix, Ariz.

-more-

j_

-67-

James A. (for Arthur) Love11, Jr., Gemini 7 pilot

BORN: ClevelanJ, Ohio, March 25, 1928

HEIGHT: 6 feet WEIGHT: 165 ibs. Blond hair, blue eyes

EDUCATION: Bachelor of Science degree from the United StatesNaval Academy, 1952; attended University ofWisconsin 1946-1948.

MARITAL STATUS: Married to the former Marilyn Gerlach ofMilwaukee

CHILDREN: Barbara Lynn, Oct. 13, 1953; James A., Feb. 15, 1955;Susan Kay, July 14, 1958

EXPERIENCE: Lovell, a Navy Lieutenant Commander, receivedflight training following his graduation from Annapolis.

He served in a number of Naval aviator assignments inclmdinga three-year tour as a test pilot at the Naval Air Test Centerat Patuxent River, Md. His duties there included service asprogram manager for the F4H Weapon System Evaluation.

Lovell was graduated from the Aviation Safety School of theUniversity of Southern California.

lie served as flight instructor and safety officer with FighterSquadron i01 at the Naval Air Station at Oceana, Va.

Lovell has logged 3,000 hours flying time, including more than2,000 hours in Jet aircraft.

CURRENT ASSIGNMENT: Lovell was selected as an astronaut byNASA in September 1962. In addition to participating in theoverall astronaut training program, he has been assignedspecial duties monitoring design and development oi" recoveryand including crew life support systems and developing tech-niques for lunar and earth landings and recovery.

Lovell is the son of Mr. and Mrs. James A. Lovell, Sr.,Edgewater Beach, Fla.

-mor©-

-68-

Edward H. (for Higgins) White II, Gemini 7 backupcommand pilot

BORN: San Antonio, Tex., Nov. 14, 1930

HEIGHT: 6 feet WEIGHT: 171 Ibs. Brown hair, Brown eyes

EDUCATION: Bachelor of Science degree from United StatesMilitary Academy, 1952, Master of Science degreein aeronautical engineering, University ofMichigan, 1959

MARITAL STATUS: Married to the former Patricia Eileen Fineganof Washington, D.C.

CHILDREN: Edward, May 15, 1953; Bonnie Lynn, Sept. 15, 1956

PROFESSIONAL ORGANIZATIONS: Associate member of Institute ofAero-space Sciences; member ofSigma Delta Psi, athletic honorary;and member of Tau Beta Pi, engi-neering honorary

EXPERIENCE: White, _ an Air Force Major, received flight train-ing in Florida and Texas, following his graduation from WestPoint. He spent 3½ years in Germany with a fighter squadron,flying F-86's and F-100's.

He attended the Air Force Test Pilot School at Edwards Air

Force Base, Calif., in 1959.

White was later assigned to Wright-Patterson Air Force Base,Ohio, as an experimental test pilot with the Aeronautical Sys-tems Division. In this assignment he made flight tests forresearch and weapons systems development, wrote technical engi-neering reports, and made recommendations for improvement inaircraft design and construction.

I_e has logged more than 3,600 hours flying time, includingmore than 2,200 hours in Jet aircraft.

CURRENT ASSIGNMENT: White is a member of the astronaut team

selected by NASA in September 1962. He was assigned as the!pilot for the second manned Gemini mission which flew for fourdays (June 3-7, 1965). White was the first U.S. astronaut totake part in extravehicular activities. He was outside theGemini _ spacecraft for 22 minutes and was the first human touse a personal propulsion unit for maneuvering in space.

White is the son of MaJ. Gen. and Mrs. Edward H. White, St.Petersburg, Fla. •

-more-

-69-

Michael Collins, Gemini 7 backup pilot

BORN: Rome Italy, Oct. 31, 1930

I_IGHT: 5 feet, i0½ inches WEIGHT: 163 ibs. Brown hairbrown eyes

EDUCATION: Bachelor of Science degree from United StatesMilitary Academy

MARITAL STATUS: Married to the former Patricia M. Finneganof Boston, Mass.

CHILDREN: Kathleen, May 6, 1959; Ann S., Oct. 31, 1961;Michael L., Feb. 23, 1963

EXPERIENCE: Collins, an Air Force Major, chose an Air Forcecareer following graduation from West Point.

He served as an experimental flight test officer at the AirForce Flight Test Center, Edwards Air Force Base, California.In that capacity, he tested performance and stability and con-trol characteristics of Air Force aircraft, primarily Jet

fighters.

He has logged more than 3,000 hours flying time, includingmore than 2,700 hours in Jet aircraft. He is a member of theSociety of Experimental Test Pilots.

Collins was one of the third group of astronauts selected by

NASA in October 1963. !

He is the son of the late MaJ. Gen. James L. Collins and Mrs.James L. Collins of Washington, D.C.

-more--

-70-

Walter M. (for Marty) Schirra, Jr., Gemini 6 commandpilot

BORN: Hackensack, N.J., Mar. 12, 1923

HEIGHT: 5 feet, i0 inches WEIGHT: 170 ibs. Brown hair,brown eyes

EDUCATION: Bachelor of Science degree, United States NavalAcademy, 1945

MARITAL STATUS: Married to the former Josephine Fraser ofSeattle, Wash.

CHILDREN: Walter M. III, June 23, 1950_ Suzanne, Sept. 29, 1957

EXPERIENCE: Schirra, a Navy Captain, received flight trainingat Pensacola Naval Air Station, Fla. As an exchange pilot withthe United States Air Force, 154th Fighter Bomber Squadron, heflew 90 combat missions in F-84E aircraft in Korea and downedone MIG with another probable. He received the DistinguishedFlying Cross and two Air Medals for his Korean service.

He took part in the development of the Sidewinder missile atthe Naval Ordnance Training Station, China Lake, Calif. Schirrawas project pilot for the PTU3 Cutlass and instructor pilot forthe Cutlass and the FJ3 _ry.

Schirra flew F311-2N Demons as operations officer of the 124thFighter Squadron onboard the Carrier Lexington in the Pacific.

He attended the Naval Air Safety Officer School at the Universityof Southern California, and completed test pilot training at theNaval Air Center, Patuxent Rive:r, Md. He was later assigned atPatuxent in suitability development work on the F4H.

He has more than 3,800 hours flying time, including more than2,700 hours in Jet aircraft.

Schirra was one of the seven Mercury astronauts named in April1959.

-more-

-71-

On Oct. 3, 1962, Schirra flew a six-orbit mission in his "Sigma7" spacecraft. The flight lasted nine hours and 13 minutes fromliftoff through landing and he attained a velocity of 17,557miles (28,200 kilometers) per hour, a maximum orbital altitudeof 175 statute miles (281 kilometers) and a total range of al-most 144,000 statute miles (231,700 kilometers). The impactpoint was in the Pacific Ocean, about 275 miles (443 kilometers)northeast of Midway Island. Me was awarded the NASA DistinguishedService Medal for his flight. He was the backup command pilotfor the Gemini 3 mission. Schirra is the son of Mr. and Mrs.,Walter M. Schirra, St., San Diego, Calif.

-more-

-72-

Thomas P. (for Patten) Stafford, Gemini 6 pilot

BORN: Weatherfordj Okla., Sept. 17, 1930

HEIGHT: 6 feet WEIGI_: 175 Ibs. Black hair, blue eyes

EDUCATION: Bachelor of Science degree from United StatesNaval Academy, 1951

MARITAL STATUS: Married to the Former Faye L. Shoemaker ofWeatherford, Okla.

CHILDREN: Dianne, July 2, 1954; Karin, Aug. 28, 1957

EXPERIENCE: Stafford, an Air Force Major, was commissioned inthe United States Air Force upon graduation from the U.S. NavalAcademy at Annapolis. Following his flight training, he flewfighter interceptor aircraft in the United States and Germany,and later attended the United States Air Force Experimental

Flight Test School at Edwards Air Force Base, Calif.

He served as Chief of the Performance Branch, USAF AerospaceResearch Pilot School at Edwards. In this assignment he wasresponsible for supervision and administration of the flyingcurriculum for student test pilots. He established basic textbooks and participated in and directed the writing of flighttest manuals for use by the staff and students.

Stafford is co-author of the Pilot's Handbook for PerformanceFlight Testing and Aerodynamic }landbook for Performance FlightTesting.

He has logged more than LJ,300 hours flying time, including morethan 3,600 hours in Jet aircraft.

Stafford was one of the nine astronauts named by NASA inSeptember 1962. He was the backup pilot for Gemini 3. Staffordis the son of Mrs. Mary E. Stafford and the late Dr. Thomas S.Stafford, Weatherford, Okla.

-more-

-73-

Virgil I. (for Ivan) "Gus" Grissom, Gemini 6 backupcommand pilot

BORN: Mitchell, Ind., April 3, 1926

HEIGHT: 5 feet 7 inches WEIGHT: 150 Ibs. Brown hair,brown eyes

EDUCATION: Bachelor of Science degree in mechanical engineeringfrom Purdue University

MARITAL STATUS: Married to the former Betty L. Moore ofMitchell, Ind.

CHILDREN: Scott, May 16, 1950; Mark, Dec. 30, 1953

EXPERIENCE: Grissom is a lieutenant colonel in the United States

Air Force, and received his wings in March 1951. He flew i00combat missions in Korea in F-86's with the 334th Fighter-

Interceptor Squadron. He left Korea in June 1952 and bec_ne aJet instructor at Bryanj Tex.

In August 1955, he entered the Air Force Institute of Technologyat Wright-Patterson Air Force Base, Ohio, to study aeronauticalengineering. In October 1956, he attended the Test Pilot Schoolat Edwards Air Force Base, Calif., and returned to Wright-Patterson Air Force Base in 1957 as a test pilot assigned to thefighter branch.

Grissom has logged more than 4,000 hours flying time, includingmore than 3,000 hours in jet aircraft. He was awarded theDistinguished Flying Cross and the Air Medal with Cluster forservice in Korea.

Grissom was named in April 1959 as one of the seven Mercuryastronauts. He was the pilot of the Mercury-Redstone 4(Liberty Bell 7) suborbital mission, July 21, 1961 and thecommand pilot of the Gemini 3 mission, March 23, 1965.

He is responsible for the Gemini group in the Astronaut Office,one of three organizational units in that office. (The othersApollo and Operations).

Grissom is the son of Mr. and Mrs. Dennis Grissom, Mitche11,Ind.

-more-

K' w !"

-74-

John W. (for Watts) Young, Gemini 6 backup pilot

BORN: San Francisco, Calif., Sept. 24, 1930

HEIGHT: 5 feet 9 inches WEIGHT: 172 ibs. Brown hair,green eyes

EDUCATION: Bachelor of Science degree in aeronauticalengineering from Georgia Institute of Technology

MARITAL STATUS: Married to the former Barbara V. White of

Savannah, Ga_

CHILDREN: Sandy, Apr. 30, 1957; John, Jan. 17, 1959

EXPERIENCE: Upon graduation from Georgia Tech, Young enteredthe United States Navy and is now a Commander in that service.From 1959 to 1962 he served as a test pilot, and later programmanager of F4H weapons systems project, doing test and evalua-tion flights and writing technical reports.

He served as maintenance officer for all-weather Fighter Squadronill3 at the Naval Air Station, Miramar, Calif. In 1962, Youngset world time-to- climb records in the 3,000 meter and 25,000meter events in the F4B Navy fighter.

He has logged more than 3,200 hours flying time, including morethan 2,700 hours in jet aircraft.

Young was among the group of nine astronauts selected by NASAin September 1962. He was the pilot of Gemini 3, March 23, 1965.

He is the son of Mr. and Mrs. William H. Young, Orlando, Fla.

-more-

-75-

PRE_IOUS GEMINI FLIGHTS

Gemini i, Apr. 8_ 1964

Unmanned orbital flightj using first production spacecraft,

to test Gemini launch vehicle performance and ability of launch

vehicle and spacecraft to withstand launch environment. Space-

craft and second stage launch vehicle orbited for about four

days. No recovery attempted.

Gemini 2, Jan. 19_ 1965

Unmanned ballistic flight to qualify spacecraft reentry

heat protection and spacecraft systems. Delayed three times by

adverse weather, including hurricanes Cleo and Dora. December

launch attempt terminated after malfunction detection system

shut engines down because of hydraulic component failure.

Spacecraft recovered after ballistic reentry into Atlantic Ocean.

Gemini 3_ Mar. 23_ 1965

First manned flight, with Astronauts Virgil I. Grissom and

John W. Young as crew. Orbited earth three times in four hours,

53 minutes. Landed about 50 miles (81 kilometers) short of plamned

landing area in Atlantic because spacecraft did not provide

expected lift during reentry. First manned spacecraft to maneuver

out of plane, after its own orbit. Grissom, who made sub-

orbital Mercury flight, is first man to fly into space twice.

-more-

-76-

Gemini 4_ June 3-7_ 1965

Second manned Gemini flight completed 62 revolutions

and landed in primary Atlantic recovery area after 97 hours,

59 minutes of flight. Astronaut James A. McD1vitt was

command pilot. Astronaut Edward H. White II was pilot,

accomplished 21 minutes of Extravehicular Activity (_A),

using a hand held maneuvering unit for first time in space.[.

Attempt to perform near-rendezvous with GLV second stage (_

failed because of insufficient quantity of maneuvering fuel.

Malfunction in Inertial Guidance System required crew to

perform zero-lift reentry.

Gemini 5, Au$. 21-29_ 1965

Longest space flight on record. Astronauts L. Gordon

Cooper and Charles (Pete) Conrad_ Jr., circled the earth

120 times in seven days, 22 hours and 59 minutes. Cooper is

first to make two orbital space flights; has more time in

space than any other human. Conrad, on first space flight,

becomes world's second most experienced astronaut. Failure

of oxygen heating system in fuel cell supply system threatened

mission during first day of" flight, but careful use of

electrical power, and excellant operational management of' fuel

cells by both crew and ground personnel, permitted crew to

complete flight ._ucce_Jully. Spaco_raft landed about ]OO

miles (161 kilometers) from primary Atlantic recovery vessel

-more-

-77-

because of erroneous base-line information programmed into

onboard computer, although computer itself performed as

planned. Plan to rendezvous with a transponder-bearing pod

carried aloft by Gemini 5 was cancelled because of problem

with fuel cell oxygen supply.

Note: Gemini 6 previously was scheduled for launch Oct. 25j

1965. The launch attempt was cancelled whenthe Agena, with

which Gemini 6 was to rendezvous, failed to achieve orbit

despite a successful Atlas booster launch.

-more-

-7g-

PROJECT OFFICIALS

George E o Mueller Associate A_linistrator_ Office of

Manne_i Space Flight, NASA Headquarters,

Acting Director, Gemini Program

LeRoy E. Day Acting Deputy Director, Gemini Program,NASA Headquarters

William C. Schneider Deputy Director, Mission Operations_

Office of Manned Space Flight, NASAHeadquarters, Gemini 7 and 6 MissionDirector

Charles W. Mathews Gemini Progr_n Manager, Mannec_

Spacecraft Center, Houston, Texas

Christopher C. Kraft Flight Director, Manned Spacecraft

Center, Houston

G. Merritt Preston Deputy Mission Director for Launch

Operations t Job_l F. Kennedy Space

Center, NASA_ Kennedy Space Center,Florida

Lt. Gen. Leighton I. Davis USAF, National Range DivisionCo_nander and D0D Manager of Manned

Space Flight Support Operations

Maj. G_n. V. G. Hasten USAF, Deputy DOD Manager and CommanderAFETR

Col. Richard C. Dineen Director, Directorate Gemini Launch

Vehicles, Space Systems Division, AirForce Systems Command

Lt. Col. John G. Albert Chief, Gemini Launch Division, 6555th

Aerospace Test Wing, Air Force Missile

Test Center# Cape Kennedy, Florida

Rear Adm. W. C. Abhau USN, Manned Spacecraft Support, •Conm_nder, Task Force 140 (AtlanticOcean Recovery Forces)

-more -

-79-

U.S. MANNED SPACE FLIGHTSMAN-hUED HOURS TOTAL MANNEDHRS.

MISSION SPACECRAFT HRS. IN MISSION CUMULATIVEHRS. MIN. SEC. HRS. MIN. SEC. HRS. MIN. SEC.

MR-3 (Shepard) 15 22 15 22 15 22

MR-4 (Grissom) 15 37 15 37 30 59

MA-6 (Glenn) 4 55 23 4 55 23 5 26 22

MA-7 (Carpenter) 4 56 05 4 56 05 l0 22 27

MA-8 (Schirra) 9 13 ll 9 13 ll 19 35 38

i

MA-9 (Cooper) 34 19 49 34 19 49 53 55 27

Gemini 3 (Grissom& Young) 4 53 00 9 46 O0 63 41 27

Gemini 4 (McDivitt& White) 97 56 ll 195 52 22 259 33 49

Gemini 5 (Cooper& Conrad) 190 56 O1 381 52 02 641 25 51

-more-

-80-

SPACECRAFT CONTRACTORS

McDonnell Aircraft Corp., St. Louis, Mo., is prime con-

tractor for the Gemini spacecraft. Others include:

AIResearch Manufacturing Co. Environment Control

Los Angeles, Calif. System

The Eagle Pitcher Co. BatteriesJoplin, Mo.

IBM Corp. Computer, GuidanceNew York, N.Y.

Northrop Corp. ParachutesNewbury Park, Calif.

Rocketdyne OAMS, RCSCanoga Park, Calif.

Thiokol Chemical Corp. Retrorocket System

Elkton, Md.

Weber Aircraft Corp. Ejection SeatsBurbank, Calif.

Westinghouse Electric Corp. _endezvous Radar SystemBalt_nore, Md.

Atlas contractors include:

General Dynamics, Convair Airframe and SystemsDiv., San Diego, Calif. Integration

R0cketdyne Div., North Propulsion SystemsAmerican Aviation, Inc.,Canoga Park, Calif.

General Electric Co., GuidanceSyracuse, New york

Titan II contractors include:

Martin Co., Baltimore Airframe and SystemsDivisions, Baltimore, Md. Integration

-raore-

-81-

Titan II contractors (cont.)

AeroJet-General Corp., Propulsion SystemsSacramento, Calif.

General Electric Co., Radio Command Guidance

Syracuse, N.Y. System

Burroughs Corp., Ground Guidance ComputerPaoli, Pa.

Aerospace Corp., Systems Engineering andE1Segundo, Calif. Technical Direction

Agena D contractors include:

Lockheed Missiles and Airframe and SystemsSpace Co., Sunnyvale, Calif. Integration

Bell Aerosystems Co., Propulsion SystemsNiagara Falls, N.Y.

McDonnell Aircraft Co., Target Docking AdapterSt. Louis, Mo.

Food contractors:

U.S. Army Laboratories, Food Formulation ConceptNatick, Mass.

Whirlpool Corp., Procurement, Processing,St. Joseph, Mich. Packaging

Swift and Co., Chicago and Principal Food ContractorsPillsbury Co., Minneapolis

Suit contractor:

The David R. Clark Co.,Worcester, Mass.

-end-